Vacuum jet manifold



Sept. 5, 1950 F. P. CHADSEY VACUUM JET MANIFOLD 4 Sheets-Sheet 1 Filed July 15, 1943 Inventor fled 6M5 and ZQMTMS Sept. 5, 1950 F. P. CHADSEY VACUUM JET MANIFOLD 4 Sheets-Sheet 2 Filed July 15, 1943' Sept. 5, 1950 F. P. CHADSEY VACUUM JET MANIFOLD 4 Sheets-Sheet s Filed July 15, 1943 Inventor Fred PC/zaasg Sept. 5, 1950 F. P. CHADSEY VACUUM JET MANIFOLD 4 Sheets-Sheet 4 Filed July 15, 1943 HHWH Inventor Patented Sept. 5, 1950 OFFICE ww-AoUuM JET MANIFOLD FredP; ohaaseyginillmo rg oalif.

I Applicati on- 'zluly 15,

l 31Glaims. 1

My invention 'z relates to i improvements simple form of manifold whieh is operative "primarily 'by' vacuumiand'adapted for awvide variety bereadily- 'understood whemthe succeeding dei scription.andclaim's "arevread with reference to 1; the drawings' accompanying and-forming part of this specification. :Intsai'ddrawings:

Figure 1 is a view in top plamipartlyibroken 4: a section, of the preferred embodiment of the manifold" detachedand :drawn :to a furtherenlarge scale, ;;-Figu-re-4 is a :view-in top plan of the same,

= Figural) is a fragmentary viewin longitudinal section of the same,

= -Figu-re6 is a viewi-n.longitudinalsection-taken on the line -66 of Figure 5,

I Figuret7-is-a detailed-view in transverse section taken ontheline of 1-4 t Figure and drawn to an enlarged scale,

Figure-8 is a-iragmentary view .in horizontal v section-taken on the line 8- 8 of- Figure?- and 1 drawn to-an enlargedscale,

Figure 9 .is a view intransverse section A on the line 99 of Figure 8,

taken T Figure 10 'is View in top plan of. a -modified embodiment of the manifold and. application uthereof, and

i g Figure ll is afragmentaryview, partly in longitudinal section} of. the modifiedlembodiment of manifold.

Referring to the drawings by numerals, by

the subject matter of my co-pendingyapplication:Serial-No.460,547 filed October -1942,

e T --which became Patent No 2 ,396, 684, March 19, 1946;. and to which attention-is invited.

-The-aeroplane, as shown in Figures A and 2, ---comprises the -i'-uselage Lmings 2 ,i-rudder --3=, tail r in A vacuum jet manifolds for distributing air orgas,

the. primary; object in 'view being vto provide a i of usea andrprindipallyras:deeicing equipment for v (Git 244-134) Y 3.: 2 v elevators 4, tailistabilizers Emandwertical fin 6. :-.The- #wings :2 1 are each .iequipped'z with'motor A na'cellea as :at I, at? the leading edge thereoi; and :sai'd amotorsi are:equipped with "/annular exhaust 1: pints 3 rcommunicatingcwith a fiat exhaust conduit 9 extendin ,i'alongv theileadingsedge or: the wing to theiuselage-l and on" top1of a sectional defrosterxeonduit .210 afitte'd on": top pf; thecwing. The conduit Jtzis sclosed :at. its outer and inner 10 ends rand .zdivicled .in its longitudinal? center, .as at l I, to iformra front Lchannel -?l2extendingc1ongiitudinal-ly of; the wing Zeand': openingsat itsi-outer end, as at 3, iintouca similanrearichann'el M, c aitsaid channels? being designed for. the circulation of. hot! exhaustr 'gases from: the motors over the .is. wing asi wi-ll beliapparent rho-prevent ic'e ifrom forming on the clawing-1 1 :The condu'it 1.0 is ar- 3 i ranged to heat: the entire wingi which it overlies, .'.-thus2. providing for de-i'cin'g of; the entire wing 0 iarea including the l leadingiedge: e'lhee'tdesign of -21"; the: conduit :iilnnay be: such as -.to :conform in anyasuitable zmannerswith the profile" of thawing so. that said conduit f Wi11'- notvpreventi the wing ifromllfunctioning .in' the usual manner. In the 5 drawings, the. conduit rill has: beenz-shown 'in a i conventional manner for the'purposeiofr'iilustraztion.

\ Accordingito my inventionai'n :its :preferred emibodimentgfla pair of manifolds lfi- 'arekpriovided 5' uponeach' side oftthefuselagei I; and are fixed to the "fuselage in;any-:suitableimanner.

' liEach manifold I'5- comprises aa transversely rectangular, tubular frontssection JS' eXtending over the? wing :2-:'CI'OSSWiS6 andt'h-avingt a closed '1 front=end'suitab1y :oonnected to thewinner end of 0* the conduit!) in communication thenewithsi and a rear end nozzle portion ll extended intoexrela- -tively.-:la-rger, similarly-shaped, tubular section I8 which, in. .turn, -extends =rearwardly= troml said nozzle portion 41 to within-a short distance of the stabilize-rs -5i-and opens -thereonandonto the elevators {it "Elie-nozzle portion-Iris centered in the-section vI B ta tspacethesame from said sec- -tion l8 and--:longitudinal-fins 19'. area provided around said nozzler portion-izlto space' said'poritiont-andsectionapartand for another purpose presently:-seen. -\The rear aseotio-n l-8=-is provided with aa reduced tubular extension 2t projecting -forward-ly to: thefront lof the aeroplane and for a purpose presently apparent. Apainoflateral branches 24,22 connect the frontisectionwlt with the=inner ends of the channels 2, -l 4 respectively, and form, as will moree-clearl-ytappear amoutlet iromsaid section i fi-xand an-inlet there/into. A

.55 forwardly*closingfliap valve -23.-.is-.hinged, as a '6 to prevent ice from forming on the same.

24, at the inner end of the branch 2I to open into said section I6 and which is provided with a suitably operating lever 25. An upwardly and rearwardly inclined, auxiliary discharge branch 26 extends from the section IB adjacent its rear end and is provided with a flap valve, as at 21, at its inner end, similar to the flap valve 23. A fan 28 is suitably mounted in the outer end of the branch 26 for operation by air and gas passing out of said branch to create a forced draft through said branch and out of the same.

Referring to the operation of the invention in the preferred embodiment and application there- V the conduit 9 into and through the section I6 to be discharged by the pressure in the section I8 out of the rear end of said section and also out of the branch 26. By partially opening the flap valve 23, as shown in full lines in Figure 8, the hot gases may be bypassed from the section I6, out of the branch 2|, into the channel I2 to return to said section I6 by way of the channel I4 and under the suction present in the section I6. Thus the appropriate wing 2 may be heated to de-ice the same. By closing the flap valve 21, the hot gases discharged from the nozzle portion I1 may be directed, under the pressure in the section I8, out of said section and past the stabilizers 5, rudders 3 and elevators 4 and the fin As will be understood, the device is designed so that the volume of atmospheric air entering the same is insufficient to cool the hot gases in the section I8 to a degree rendering the same ineffective as a de-icing agent. By closing the flap valve 23 and opening the flap valve '21, the hot gases from the conduit 9 may be discharged into the atmosphere out of the branch 26, as when deicing is not required. The fan 26 operates to create a boosting suction in the sections I6, I8.

If desired the exhaust pipes 8 may be provided with flap valves 8a adapted for opening to the atmosphere by connections, indicated in dotted lines at 822, to operating hand wheels 80 all for the purpose of controlling the passage of hot gases from the exhaust pipes 8 to the manifold as, for instance, by cutting out any desired exhaust pipe or varying the volume issuing'therefrom.

r In the case of an aeroplane having a single motor 29 in the nose thereof, as shown in Figure 10, the front section 30 of the manifold maybe directly connected at its front end' to an exhaust pipe 3| of the motor 29 instead of toa conduit such as 9. In Figure 10, the wing 32 is provided therein with channels 33, 34 similar to channels I2, I4 and discharge and inlet branches 35, 36 extend from said section 30 and communicate with said channels 33, 34, respectively. Otherwise the construction and operation is the same as that described with reference to the preferred embodiment of the invention.

The foregoing will, it is believed, sufiice to im-' part a clear understanding of my invention without further explanation.

4 scribed, without departing from the inventive concept, the present disclosure is to be construed as illustrative only, and right is herein reserved to modifications falling within the scope of the appended claims.

What I claim is:

1. The combination with a motor powered airplane having a fuselage and wings, of a pair of longitudinal defroster conduits on one wing intercommunicating at the outer ends of the wing and terminating at" said fuselage, a conduit on said wing for receiving exhaust gasses from the motors, a tail stabilizer on said fuselage, a manifold including a tubular section extending alongside said fuselage beneath said wing with an open front end for taking in air when the airplane is in flight and having a rear discharge end opening onto said stabilizer, said manifold further including a second tubular section extending over said wing from said exhaust conduit into said first section intermediate the ends of said first section and terminating in said first section in a nozzle in concentric spaced relation to said first section with an open rear end whereby air passing through said first section creates a suction behind said nozzle causing suction in the second section whereby exhaust gasses are drawn through said second section and forced out of said nozzle in jet form to heat the air passing through the first section and force the same out of said discharge end for de-icing said stabilizer, and valve controlled means for bypassing gasses out of said second section into one defroster conduit and from the other defroster conduit back into said second section to thereby defrost said wing.

2. The combination with a motor powered airplane having a fuselage and wings, of a pair of longitudinal defroster conduits on one wing intercommunicating at the outer ends of the wing and terminating at said fuselage, a conduit on said wing for receiving exhaust gases from the motors, a tail stabilizer on said fuselage, a manifold including a tubular section extending alongside said fuselage beneath said wing with an open front end for taking in air when the airplane is in flight and having a rear discharge end opening onto said stabilizer, said manifold further including a second tubular section extending over said wings from said exhaust con- -duit into said first section intermediate the ends of said first section and terminating in said first section in a nozzle in concentric spaced relation to said first section with an open rear end whereby air passing through said first section creates a suction behind said nozzle causing suction in the second section whereby exhaust gases are drawn through said second section and forced out of said nozzle in jet form to heat the air passtion and adapted for other uses than those de-' ing through the first section and force the same out of said discharge end for de-icing said stabilizer, and valve controlled means for bypassing gases out of said second section into one defroster conduit and from the other defroster conduit back into said second section to thereby defrost said wing, said first section being provided with means in the rear of said nozzle for directing the heated air out of the same away from said stabilizer when de-icing of the stabilizer is not desired.

3. A manifold for use with a source of hot gas to convey the same from said source for heating purposes, said manifold comprising a straight tubular section for passing air therethrough and having open intake and discharge ends,-a second tubular section for passing hot gas therethrough having an end spaced to one side of the first section for connection to said source, said second section inclining into the first section intermediate the ends of the first section and terminating in said first section in a nozzle spaced from and concentric to said first section whereby gas passing through said second section and out of said nozzle creates a suction in said first section around said nozzle to draw air into the intake end of said first section to be heated by the hot gas issuing from said nozzle and forced out of the discharge end of said first section for use for heating purposes, and valve controlled means for said first section adjacent the discharge end thereof for passing the heated air out of said first section to atmosphere before it reaches the discharge end to thereby control discharge out of said discharge end.

, FRED P. CHADSEY.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS 

